Floating missile launcher



May 26, 1970 s. J. PENZA FLOATING MISSILE LAUNCHER Filed June 24, 1968 28 26 Fig.

NOZZLES THRUSTING MOTION Fig.4

INVENTOR. SALVATORE J. PENZA BY go tw a W 29%. T TOR/V575 States Patent 3,513,750 FLOATING MISSILE LAUNCHER Salvatore J. Penza, Oxnard, Calili, assignor to the United States of America as represented by the Secretary of the Filed June 24, 1968, Ser. No. 739,332

Int. Cl. F411 3/04 U.S.Cl. 89-1309 4 Claims ABSTRACT OF THE DISCLOSURE The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the payment of any royalties thereon or therefor.

BACKGROUND OF THE INVENTION Field of the invention The present invention relates to missile launching means and in particular to floating launchers intended for launching missiles from the open sea. It is also directed to means for orienting such a launcher so that a missile may be launched in any desired direction.

Description of the prior art Prior devices employed for launching missiles from the sea primarily employ a tube or missile encircling framework including a plurality of missile guiding rails. A large flotation collar mounted at the forward end thereof provides the buoyant force necessary to float the launcher and missile. When launched, the missile exits through the collar. Guidance is ordinarily not imparted to prior art sea launched missiles until after the missile is airborne.

Serious obstacles exist in sea launch operations. Usually the missile very large and cumbersome; which creates buoyancy and maneuverability problems. Furthermore, since an attached missile must exit unencumbered from the surrounding structure, most prior buoyant launchers launch only onesize or type of missile. Also, prior buoyant launching devices do not usually incorporate elevation and azimuth control means and hence means must be provided in each missile for imparting guidance information during flight.

SUMMARY OF THE INVENTION The present invention comprises a lengthy buoyant keel which floats in an upright, substantially vertical orientation with a missile launching rail located along one vertical side: An elevation and azimuth sensing system controls a series of position correction propulsive devices mounted at suitable locations on the keel and designed to control the launch elevation and azimuth position.

It is an object of the present invention to provide an improved buoyant device for launching missiles from a body of water.

Another objeet is to provide a buoyant sea launching device of relatively moderate size and weight but capable of handling missiles of various types and sizes.

A further object is to provide a buoyant sea launching Patented May 26, 1970 "ice device having a stabilizing mechanism for orienting the device in a desired elevation and azimuth position.

Another object is to provide a sea launch system where launch information is imparted to the system up until the very moment of launch.

Other objects, advantages, and novel features of the invention will become apparent from the following detailed description of the invention when considered in conjunction with the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWING FIG. 1 is a side elevational view of the invention with a missile shown in place.

FIG. 2 is a top plan view of the launcher of FIG. 1.

FIG. 3 is an enlarged transverse sectional view taken along a line substantially corresponding to line 33 of FIG. 1.

FIG. 4 is a chart showing relative launcher keel movement with various control jet operations.

DESCRIPTION OF THE PREFERRED EMBODIMENT Referring to the drawing, wherein like reference numerals designate like parts, there is shown an elongate buoyant launcher 10 floating in an upright and substantially vertical orientation in a body of water with a missile 12 attached to one vertical side thereof.

The launcher 10 includes a watertight buoyant and elongate tubular keel 14 which may be constructed of any suitable lightweight material. The keel 14 is lighter than the water it displaces and has adequate buoyancy to support a missile 12 when attached. A missile launch rail 16 may be provided along one elongate vertical side of the keel 14 and receives in conventional fashion mounting lugs 18. At launch the missile will move upwardly along rail 16 until it becomes airborne.

A series of valves 22, 24, 26 and 28 are positioned at the lower end of keel 14 and control discharge of a suitable jet through nozzles 30, 32, 34 and 36. Mounted in any desired location on the launcher 10 but preferably near the upper end of the tubular keel 14 is an elevation and azimuth sensing device 20 which is adapted to send a programmed signal to a servo unit 38 positioned within the keel 14 to actuate selected valves or combinations of valves 22, 24, 26, 28 and operate the corresponding propulsive jets 30, 32, 34, 36 to orient the launcher in accordance with the desired elevation and azimuth positioning.

The sensing device 20 may be controlled, if desired, from a ship or land station by a suitable transmitterreceiver 40 positioned adjacent the sensing device. Such a programming signal is relayed via the servo unit 38 which operates one or more of the valves 22, 24, 26, 28 and actuates the corresponding jet 30, 32, 34, 36 for desired directional positioning of the launcher 10.

The propulsive jets may be powered by air stored under pressure in a tank 42 in the hollow keel 14. However other means of thrust may be employed such as jets of water under pressure, propellers, etc. Thus, by controlling the operation of the propulsion devices, azimuth and elevation of the launcher can be controlled to provide stability at a desired launch position.

An electrical power pack 44 may be positioned within the keel 14 to supply power for operation of the transmitter-receiver 40 and other power operated units.

Thus in launching a missile from the present invention, the desired directional information is programmed into the sensing device 20 or is transmitted thereto by a suitable transmitter-receiver connection with a ship or shore monitoring station. The sensing device 20 signals the servo unit 38 which operates valves 22, 24, 26, 28 and actuates the proper propulsive jets 30, 32, 34, 36 to provide the 3 necessary elevation and azimuth positioning to the keel and the missile 12. FIG. 4 demonstrates some of the launcher motions achieved with different combinations of nozzle jets and it will be apparent that with this arrangement any desired positioning of the launch rail can readily be achieved. The missile 12 is then launched in the desired direction.

If desired an access hatch 46 may be provided to permit manual presetting of elevation and azimuth information into the system where the radio control is not to be employed.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. A floating missile launcher comprising:

a buoyant keel of elongated configuration substantially vertically disposed in a body of water;

a missile launching rail extending along one external side of the keel and upon Which a missile is positioned, said rail adapted to guide the missile from the keel in the direction of orientation; and

deflection means for applying to said elongated keel prior to launching of said missile at least one force acting in a plane essentially normal to the longitudinal axis of said keel so as to orient said missile in a desired azimuthal position and/ or at a desired angle of elevation other than vertical.

2. A floating missile launcher as defined in claim 1 wherein said deflection means includes:

a directional sensing device mounted on the keel;

a plurality of propulsion nozzles mounted about the periphery of said keel;

said sensing device being the controlling means for actuating the propulsion nozzles to orient the launcher and attached missile in accordance with the desired elevation and azimuth positioning.

3. The floating launcher of claim 2 wherein said propulsion nozzles are powered by air pressure stored in said keel.

4. The floating launcher of claim 2 wherein said sensing device is controlled by radio means for actuating the propulsion nozzles to stabilize the launcher and attached missile in a desired position.

References Cited UNITED STATES PATENTS 3,373,657 3/1968 Guin 89-1.81 3,153,979 10/1964 Villers 891.809 3,245,318 4/1966 Finkelstein et al. 891.809 3,295,411 1/1967 Lehmann 89-l.81 3,301,132 1/1967 Lehmann et al. 89l.81

SAMUEL W. ENGLE, Primary Examiner US. Cl. X.R. 891.8l9 

